Mission Description

This is a fast (2 year) sample return (rendezvous at both ends).

• Propulsion System:
• SEP, Solar Array ASPA 1,
• Engine NSTAR Engine G (1 Engine), Duty Cycle 100%, P0 = 11 kW
• Launch Date, any time in 2010: Jan 1 2010 ≤ tlaunch ≤ Dec 31 2010
• Arrival Date is such that return date is no more than 2 years after the launch date:  tarrival - 730 days ≤ tlaunch
• The return is a Rendezvous with the Earth; i.e., return V infinity = 0
• Tempel 1 Stay Time, no less than 45 days:  tstay ≥ 45 days
• Mass Drop 0 (fixed)
• Launch Vehicle Delta II 7326-9.5
• V infinity magnitude and direction are free to be optimized.
• Originally Modeled in Copernicus

Input/Output files

Copernicus20060313.zip (download)